Multivariable Sliding-Mode Strategy with Output Constraints for Aeroengine Propulsion Control

Du, Xian; Richter, Hanz; Guo, Yingqing

doi:10.2514/1.g001802

Cited by 39 publications

(19 citation statements)

References 24 publications

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“…In recent years, it has been widely used in commercial aero-engines [2][3][4][5]. For the Min-Max control strategy, current mainstream research interests mainly include the following three points: one is the controller design method to improve the control performance of the Min-Max scheme, such as applying a sliding mode controller to replace a linear controller to improve the limit protection control [6][7][8][9][10]. However, the changes proposed in this study necessitate a complete redesign of the engine controller, which will impose challenges in terms of verification across the whole operating envelope and acceptance by engine control implementers [1].…”

Section: Introductionmentioning

confidence: 99%

An Output-Based Limit Protection Strategy for Turbofan Engine Propulsion Control with Output Constraints

Qin

Pan

et al. 2019

Energies

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To accomplish the limit protection task, the Min-Max selection structure is generally adopted in current aircraft engine control strategies. However, since no relationship between controller switching and limit violation is established, this structure is inherently conservative and may produce slower transient responses than the behavior by engine nature. This paper proposes an output-based limit management strategy, which consists of the safety margin module and the parameter prediction module to monitor system responses, plus the switching logic to govern switches between the main controller and limiters, and, in this way, a faster transient performance is achieved, and the limit protections in transient states become more effective. To realize smooth switching control, the linear-quadratic bumpless transfer method is developed. The design principle of the multi-loop switching control and bumpless compensator is detailed, and the effect-on limit protection control performance-of the design parameters in the safety margin and parameter prediction modules are also analyzed. The proposed approach is tested using simulations covering the whole flight envelope on the nonlinear component-level model of a turbofan engine, and the superiority over the Min-Max architecture is also validated.

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Section: Introductionmentioning

confidence: 99%

An Output-Based Limit Protection Strategy for Turbofan Engine Propulsion Control with Output Constraints

Qin

Pan

et al. 2019

Energies

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“…In [3], conditional active limit regulators are added on the Min-Max architecture. Numerous candidates have also been applied to design the regulators for Min-Max architecture such as sliding mode control [4,5] and monotonic control [6]. However, a large number of technologies with limited protection functions that are not based on the Min-Max structure have been developed for aircraft engines.…”

Section: Introductionmentioning

confidence: 99%

Reference and Limit Governors for Limit Protection of Turbofan Engines

Pan

Qin

et al. 2019

Energies

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This paper proposes a novel architecture of limit protection including the references governors and limit governors and applies this architecture to limit protection in turbofan engines. References governors are designed as add-on schemes to a pre-stability engine control system that modifies reference commands to avoid constraints violation. Limit governors are proposed as an assistant part for references governors adjusting constraints to prevent references from stopping updates. The use of output admissible sets for a class of variable constraints is exploited to form invariant sets. Simulation results based on a turbofan engine model show that references governors with limit governors can effectively enforce the multiple constraints and provide enhanced engine thrust when steady violation occurs.

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“…The control problem and diagnosis problem of smallrange fluctuation near the steady state point are the current research hotspots [5][6][7]. It not only needs to improve the control algorithm, the design methods of the observer, and the estimation method of model uncertainty [8,9] but also needs to improve the model to expand the application range of the linear model. The purpose of developing the application range of the linear model is to make the model more accurate within a wide range of state parameters.…”

Section: Introductionmentioning

confidence: 99%

Study on Identification Method for Parameter Uncertainty Model of Aero Engine

Bai

Shuai

Wang

2019

International Journal of Aerospace Engineering

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The linear model of an aero engine is effective in a small range of the neighborhood of equilibrium points. According to this problem, the identification method for the parameter uncertain linear model of the aero engine was proposed. The identification problem is solved by calculating nonlinear programming. Considering the parameter uncertainty of the model is the critical point of this research during the optimization process. A parameter uncertain model of an aero engine can be obtained, which has large use range. This method is used for DGEN380 aero engine. The two parameters, VDD and VE, are defined for describing error range. Compared with experimental data, the uncertain model of DGEN 380 can simulate the real state of DGEN380 within 1% error range when ΔPLA < 22%. Compared with another conventional method of identification (recursive least squares), the parameter uncertain model, established by the method of this research, has a broad application area through parameter uncertainty of the model.

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Multivariable Sliding-Mode Strategy with Output Constraints for Aeroengine Propulsion Control

Cited by 39 publications

References 24 publications

An Output-Based Limit Protection Strategy for Turbofan Engine Propulsion Control with Output Constraints

An Output-Based Limit Protection Strategy for Turbofan Engine Propulsion Control with Output Constraints

Reference and Limit Governors for Limit Protection of Turbofan Engines

Study on Identification Method for Parameter Uncertainty Model of Aero Engine

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